This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Double Bypass Turbofan Engine Modeling including Transient Effects
ISSN: 0148-7191, e-ISSN: 2688-3627
Published November 02, 2010 by SAE International in United States
Annotation ability available
Event: Power Systems Conference
Modern military engines desire both the fuel efficiency of high-bypass turbofans and the high specific thrust of a low-bypass turbofan. Using traditional engine architectures, performance and efficiency are in conflict, so an engine is usually designed to best meet requirements for its primary mission. While the concept of a variable cycle engine is not new, recent advances in engine architecture technology suggest that adding a second bypass stream to a traditional turbofan can provide significant benefits. This “third stream” (the core flow being the primary stream and the inner bypass being the second stream) airflow can be independently modulated so that engine airflow demand can be matched with the available inlet flow at a variety of operating points, thereby reducing spillage drag. Additionally, the third stream air provides a valuable heat sink for cooling turbine cooling air or dissipating other aircraft heat loads. While the potential benefits of this architecture are clear, the transient stability and performance of such an engine has not been thoroughly evaluated. This research strives to characterize the dynamic response of a three stream engine while capturing various transient effects and to assess the computational burden of each effect.
|Technical Paper||Impact of Heat Exchanger Location on Engine Performance|
|Technical Paper||Test Evaluation of an Affordable Fighter Aircraft Vapor Cycle System|
|Technical Paper||Variable Cycle Optimization for Supersonic Commercial Applications|
CitationCorbett, M. and Wolff, M., "Double Bypass Turbofan Engine Modeling including Transient Effects," SAE Technical Paper 2010-01-1800, 2010, https://doi.org/10.4271/2010-01-1800.
- Simmons, R. “Design and Control of a Variable Geometry Turbofan with an Independently Modulated Third Stream,” Aerospace Engineering Department, The Ohio State University Columbus, Ohio 2009
- “Performance Prediction and Simulation of Gas Turbine Engine Operation for Aircraft, Marine, Vehicular, and Power Generation,” NATO RTO Applied Vehicle Technology Panel (AVT) Task Group AVT-036 February 2007
- “NPSS User Guide,” NASA Glenn Research Center (NPSS/NICE) March 2008
- Lytle, J. “The Numerical Propulsion System Simulation: An Overview,” NASA/TM-2000-209915 Cleveland, Ohio June 2000
- Jones, S. “An Introduction to Thermodynamic Performance Analysis of Aircraft Gas Turbine Engine Cycles Using the Numerical Propulsion System Simulation Code,” NASA/TM-2007-214690 Cleveland, Ohio March 2007
- Turner, M. Reed, J. Ryder, R. Veres, J. “Multi-Fidelity Simulation of a Turbofan Engine With Results Zoomed Into Mini-Maps for a Zero-D Cycle Simulation,” NASA/TM-2004-213076 Cleveland, Ohio November 2004
- Mattingly, J. Heiser, W. Pratt, D. Aircraft Engine Design Second Reston, Virginia 2002
- Walsh, P. Fletcher, P. Gas Turbine Performance Second Blackwell Science Ltd Maiden, Mass. 2004
- “NPSS Humidity Addendum,” ASA Glenn Research Center (NPSS/NICE) March 2008
- “NPSS Reynolds Addendum,” NASA Glenn Research Center (NPSS/NICE) March 2008